Method for eliminating sources of error in the system correction of a coordinate measuring machine

ABSTRACT

A method is disclosed for eliminating sources of error in the system correction of a coordinate measuring machine. Herein, a number j of reference structures  33  on a rigid reference object  30  are measured in a starting orientation k=0, and the starting coordinates and the reference coordinates of the reference structures  33  on the reference object  30  are determined in a number k&gt;3 of mutually different orientations.

The present invention relates to a method for eliminating basic error sources in a system correction of a device for 2D metrology.

At least one illumination means is provided for a device for 2D metrology. For the purpose of measuring the position of an object or of a structure on a substrate (mask for the semiconductor industry or wafer), at least one laser interferometer system is used to determine a position displacement of an object or the structure in at least one spatial direction. The at least one laser interferometer system is housed in a climatized chamber together with the object and the entire device for 2-D metrology.

A measuring unit for measuring structures on masks or substrates used for the production of semiconductors is described in detail in the lecture manuscript “Pattern Placement Metrology for Mask Making” by Dr. Carola Bläsing given on the occasion of the Semicon Education Program congress in Geneva on 31 Mar. 1998. The description therein forms the basis for the Leica LMS IPRO coordinate measuring unit of the applicant. For details regarding the mode of operation and the construction of this measuring unit, reference is made to the publication cited as well as to the devices on the market (currently Leica LMS IPRO 3). Because the present invention may be advantageously used with such a measuring unit, and—without loss of generality—is primarily described in connection with such a measuring unit. In the context of the present application, the terms “sample,” “substrate,” and the general word “object” are used interchangeably. In the production of semiconductor chips, which are arranged on wafers, the structure widths of the individual structures become ever smaller as a result of ever greater packing density. Accordingly, the specification demands of coordinate measuring units that are used as measuring and inspection systems for measuring the edges and the position of structures, and for measuring the structure widths, are increasing. Now as before, optical sampling methods are favored in these measuring units, although the required measurement accuracy (currently in the range of a few nanometers) is far below the resolution achievable with the light wavelengths in use (near UV spectral range). The advantage of optical measuring units is largely their less complicated construction and easier operation in comparison to systems with different sampling, e.g., x-ray or electron beams.

In order to achieve the required nanometer accuracy in structure measurement, it is important to minimize as much as possible interfering influences from the environment, such as changes in ambient air or vibrations. For this purpose, the measuring unit may be housed in a climatized chamber, which regulates the temperature and humidity in the chamber with great precision (<0.01° C. and <1% relative humidity, respectively). To prevent vibrations, the measuring unit 1 is—as aforementioned—mounted on a granite block with vibration dampers.

As a rule, the positions of such structural elements are determined relative to a reference point on the substrate (mask or wafer) or relative to the optical axis. The coordinates of the structure are obtained from this together with the position of the interferometrically measured measuring stage. The structures on wafers or the masks used for exposure permit of only extremely small tolerances. Very high measuring accuracy (currently in the nanometer range) is therefore required when testing the structures. A method and a measuring unit for determining the position of such structures is known from German patent application DE 100 47 211 A1. For details regarding position determination, reference is made to this application.

German patent DE 197 34 695 C1 relates to a method for determining a correction function for elimination of coordinate-dependent measuring errors in a coordinate measuring machine through self-calibration. The invention is based on the realization that there are special components of the correction function which are not unambiguously determined or are subject to very large errors. This mainly concerns components which, in the calibration measurements of all orientations of a reference object used for the calibration, always coincide with themselves (exactly or only approximately), i.e. the rotationally symmetrical components are invariant for the rotations of the reference object that are carried out.

U.S. Pat. No. 4,583,298 describes the self-calibration of a coordinate measuring machine with the aid of a calibration plate, on which a grid is arranged. The positions of the grid points are not calibrated, however. The grid plate is laid on the object stage of the coordinate measuring machine and the positions of its grid points are measured. The same grid plate is then further rotated two or more times through, respectively, 90° about a rotation axis and, in each of the set orientations, the positions of the grid points are measured. The measuring results are mathematically rotated in reverse and various correction factors and stages are optimized so that the reverse rotated data sets have a better agreement. U.S. Pat. No. 4,583,298 concerns itself in detail with the problem of faulty or unreliable corrections. The cause has been identified as being errors in the measuring of the measurement values used for correction determination. It is shown that a mathematically unambiguous correction is only achieved when more than two different rotation positions are measured with the same grid plate. For this purpose, the grid plate is laid, as previously known, on the object stage and the positions of its grid points are measured in a plurality of orientations of the grid plate. The orientations are achieved, for example, by multiple rotation through 90° about their mid-point. However, the grid plate must then be displaced to a totally different position on the object stage. Once there, the measurement of the positions of its grid points is repeated in a plurality of orientations, as previously known. It is essential herein that the same grid plate must be displaced on the object stage.

U.S. Pat. No. 5,798,947 discloses a method for self-calibration of stages of a 2-D metrology measuring machine. A plate comprising an N×N grid of marks is used in order to determine the stage positions relative to a Cartesian coordinate system. From this a rotation function Gx(x,y) and Gy(x,y) is determined. For the self-calibration, the mask is rotated through respective 90° steps. In addition, measurement with a displaced mask is carried out. Based on the teaching of U.S. Pat. No. 5,798,947, it is not possible to determine error components that provide the same distortion in all the individual measurements. With a displacement of the mask by {right arrow over (y)} functions which, on rotation about an axis by 90° and additional displacement by {right arrow over (y)}, coincide with themselves.

A transmitted light illumination device with a height adjustable condenser 17 and a light source 7 is fitted in the granite block 23, the light of which is received via an enlarging coupling optics 3 with a preferably large numerical entrance aperture. A particularly large amount of light from the light source 7 is captured in this manner. The captured light is coupled with the coupling optics 3 in an optical waveguide 4 such as fiber-optic bundle. An outcoupling optics 5, which is preferably implemented as an achromatic optics, collimates the light emitted by the fiber optic 4.

In order to achieve the required nanometer accuracy in structure measurement, it is important to minimize as much as possible interfering influences from the environment, such as changes in ambient air or vibrations. For this purpose, the measuring unit may be housed in a climatized chamber, which regulates the temperature and humidity in the chamber with great precision (<0.01° C. and <1% relative humidity, respectively). To prevent vibrations, the measuring unit 1 is—as aforementioned—mounted on a granite block with vibration dampers 24, 25.

The accuracy of position determination of the structures depends greatly on the stability and accuracy of the laser interferometer system used to determine the X/Y stage position. Because the laser beams from the interferometer expand in the ambient air of the measuring unit, the wavelength is dependent on the refraction index of this ambient air. This refraction index varies with changes in temperature, humidity, and air pressure. In spite of temperature and humidity regulation in the climatized chamber, the residual variations in wavelength are too high for the required measurement accuracy. An etalon is therefore used to compensate for measurement changes resulting from changes in the refraction index of the ambient air. In such an etalon, a measuring beam advances a defined metric length so that changes in the correspondingly measured optical length may only be caused by changes in the diffraction index of the ambient air. As a result, etalon measurement largely compensates for the influence of changes in the diffraction index in that the current value of the wavelength is determined continuously and taken into account for the interferometric measurement.

It is therefore an object of the present invention to provide a method with which sources of error in the system correction of a coordinate measuring machine can essentially be eliminated.

A suitable analysis of an individual measurement permits the recognition of mismeasurements so that a repeat measurement need only be performed in this case. As a result, the throughput of the machine is only minimally reduced and will normally not be noticed by the customer.

This object is achieved according to the invention by a method which, for a number j of reference structures on a rigid reference object in a starting orientation k=0 of the reference object, determines the coordinates of the reference structures. The different orientations are set by at least two rotation about one axis, in each case, and at least one displacement, and it least one displacement or by rotating about it least one axis and at least two different displacements.

Exemplary embodiments of the invention will now be described and their advantages will be explained in greater detail by reference to the accompanying drawings, in which:

FIG. 1 shows schematically a coordinate measuring device according to the prior art;

FIG. 2 shows an error image which, on rotation by 90° and displacement, coincides with itself;

FIG. 3 shows a possible configuration of an embodiment of a reference object.

FIG. 4A shows the reference object in a starting orientation k=0.

FIG. 4B shows the reference object in an orientation k=1 generated by rotation.

FIG. 4C shows the reference object in an orientation k=2 generated by another rotation about another rotation axis.

FIG. 4D shows the reference object in an orientation k=3 generated by a displacement.

FIG. 5A shows the reference object in a starting orientation k=0.

FIG. 5B shows the reference object in an orientation k=1 generated by a rotation.

FIG. 5C shows the reference object in an orientation k=3 generated by a first displacement.

FIG. 5D shows the reference object in an orientation k=3 generated by a second displacement.

FIG. 1 shows a coordinate measuring device as has long been known from the prior art for the measuring of structures on masks and/or wafers.

Objects 2 may be optically inspected with the embodiment of the invention shown in FIG. 1. The object 2 may be a mask which, for example, may be comprised of quartz glass. Structures 3, which are to be inspected by the measuring device 1, are applied to the mask. The measuring device 1 comprises two illumination beam paths 4 and 5, whereby the illumination beam path 4 is provided for the transmitted light mode and the illumination beam path 5 for the incident light mode. A light source 6 is provided for the transmitted light mode, which emits light in the near UV range, and which is reflected by the mirror 7 in the direction of an illumination optics implemented in the form of a condenser 8. The light from the illumination beam path 4 passes through the object 2 and is collected, at least in large part, by the imaging optics 9 and imaged on the detector 10. The detection beam path 11 thus extends from the object 2 to the detector 10, whereby the light coming from the object 2 is almost entirely reflected by the beam splitter 12 in the direction of the detector 10. The imaging optics 9 can be translated by a focusing device, which is not shown in the figure, along the z-direction indicated by the double arrow, by which means the object 2 or the structures 3 may be focused. The condenser 8 may be translated along the z-direction in the same fashion.

The measuring device 1 also has an incident light mode. In this mode, illumination of the object 2 is achieved with light from the light source 13, which largely passes the beam splitter 12 and illuminates the object 2 via the illumination optics 9. The illumination light that reflects on the object 2 or on the structures 3 in this mode passes through the imaging optics 9 in the opposite direction and is also reflected by the beam splitter 12 in the direction of the detector 10. Accordingly, the illumination beam path 5 extends from the light source 13 to the object 2. The illumination beam path 4 extends from the light source 6 to the object 2.

The imaging optics 9 is a high-resolution, apochromatically corrected microscope optics, which is designed for light in the UV range. The detector 10 is implemented in the form of a high-resolution CCD camera and is controlled and read by a first computer evaluation and analysis system 100, which is shown in FIG. 1.

According to the invention, the measuring device 1 has a means implemented in the form of a filter 14 and 15, one of which is arranged in the illumination beam path 4 and on the other in the illumination beam path 5. The filter 14 is arranged in the pupil plane of the illumination optics, which is implemented in the form of the condenser 8 in the illumination beam path 4. The filter 15 is arranged in the pupil plane of the imaging optics 9 of the illumination light beam 5. In this respect, the filter 15 also acts in the detection beam path of 11 because, for example, in this exemplary embodiment it is not arranged between the light source 13 and the beam splitter 12.

The object 2 is mounted on a positioning means implemented in the form of a measuring stage, and translatably mounted along the different x- and y-directions indicated with the two double arrows. The positioning means 18 has a frame in which the object 2 is placed. The laser interferometry system 22, with which the position of the positioning means 18 may be measured interferometrically via the light beam 23, is merely schematically indicated. The frame of the positioning means 18 is here mounted on an air pillow and can be translated all but frictionlessly on the granite block 20. The granite block 20 itself is mounted vibration-damped on the bases 21.

FIG. 2 shows an error image for rotations by 90° which, on displacement, for example, by the vectors shown and rotation by 90°, coincides with itself. In Method claimed by the patent DE 197 34 695 C1, for a rotation axis separation {right arrow over (x)}, all the functions coincide with themselves on rotation about the two rotation axes and through 90°. U.S. Pat. No. 5,798,947 describes a displacement of the mask by {right arrow over (y)} functions which, on rotation about an axis by 90° and additional displacement by {right arrow over (y)}, coincide with themselves.

If, for example,

$\overset{\rightarrow}{x} = {\overset{\rightarrow}{y} = {\begin{pmatrix} 0 & s \end{pmatrix}^{T} = \begin{pmatrix} 0 \\ s \end{pmatrix}}}$

then a non-identifiable error component for both methods is given by:

${\overset{\rightarrow}{f}\left( {x,y} \right)} = {{\begin{pmatrix} {\sin \left( {k \cdot y} \right)} \\ {- {\sin \left( {k \cdot x} \right)}} \end{pmatrix}\mspace{14mu} {for}\mspace{14mu} k} = \frac{2\pi}{s}}$

This results in the error image shown in FIG. 2 which coincides with itself both for rotations by 90° and also for displacements by the vector {right arrow over (x)}. Further displacements with invariance are also shown in FIG. 2. There are many other invariant error components. In the example shown in FIG. 2, these are, for example, all functions with whole-number multiples of {right arrow over (k)}.

FIG. 3 shows a rigid reference object 30 which, in order to carry out a self-calibration in the starting orientation k=0, is laid on the measuring table 20 of the coordinate measuring machine 1. The current orientation of the reference object 30 is indicated by a marking 34. In the starting orientation, this appears in the lower left corner of the reference object 30. The reference object 30 is selected to be large enough so that it covers the entire measuring range of the coordinate measuring machine and, accordingly, covers almost the entire displacement range of the measuring table 20.

A common mask holder which is not shown for reasons of simplification, designed for the measuring of masks serves to accommodate the reference object 30. It is thus known to mount the mask in restraining force-free manner on three support points. It is also conceivable that the reference object 30 is inserted directly and without a mask holder in the measuring table 20. The bending produced by its own weight is calculated and, reckoned out of the measured coordinates of the structures 33 on the mask. Other mask holders draw the mask down with vacuum feet. However, this generates bending of the mask that cannot be precisely described. In the example under consideration, the reference object 30 (and later, other reference objects) is always laid abutting the lower edge of the measuring table 20, which also serves as a support for the masks to be measured and for which displaceable support points for different mask sizes are available. On the reference object 30, a number j of reference structures 33 is selected, the coordinates of which should be measured for carrying out the self-calibration. Although lines are shown as reference structures 33 for the reference object shown in FIG. 3, it is obvious to a person skilled in the art that the reference structures 33 can also have other forms.

The fundamental concept of the invention is illustrated in FIGS. 4A to 4B and FIGS. 5A to 5B. Further measurements with a further rotation axis or a further displacement vector can be added thereto. The non-determinable error components must have, for all these measurements, the property in common that they coincide with themselves for the rotations and the various displacements. Thus the non-determinable error components are always more distinctive. In the case of the sine function described above, the error component is invariant for displacements s and t in the X-coordinate or the Y-coordinate directions. If, to a good approximation, the following applies: there are natural numbers n, m for which

${\frac{m}{n} \cong \frac{s}{t}},$

then k is chosen such that

$k = \frac{2\pi \; m}{s}$

or (almost equivalent)

$k = {\frac{2\pi \; n}{t}.}$

In concrete terms, s=14 mm and t=10 mm, so that at least m=7 and n=5. Thus

$k = {\frac{2\pi \; 7}{14\mspace{11mu} {mm}} = {{\pi \mspace{11mu} {mm}^{- 1}} = {\frac{2\pi \; 5}{10\mspace{11mu} {mm}}.}}}$

This corresponds to a period length of 0.5 mm or a whole-number fraction thereof.

This procedure appears initially to be relatively unhelpful, since the wavelength of the non-observed error sources is merely reduced, but they are not themselves eliminated. However, these invariant error components are a problem of self-calibration that is practically insoluble. It can be assumed, however, from the technical structure of a coordinate measuring device that very short wavelength error components are practically unable to occur. Thus, for example, short-wavelength unevenness in the mirrors within the beam diameter of an interferometer beam (typically 4 mm) are averaged or guidance errors are suppressed by the diameter of the air bearings of a few centimetres to small length scales.

Thus, practically all the error components occurring are detectable and therefore correctable. The self-calibration is measured based on substrate measurements in at least two different orientations which differ by 90°, and a displacement. Also, substrate measurements in rotation positions about a second rotation axis and a displacement are conceivable.

FIG. 4A shows that initially the reference object 31 is placed in the starting orientation on the mask holder. In this starting orientation k=0 of the reference object 30, the starting coordinates (of the position vector) {right arrow over (r)}_(1j0) of the j selected reference structures 33 are measured. Thereafter, as shown in FIG. 4B, the reference structures 33 of the reference object 30 are measured in at least one other orientation of the reference object 30. For this purpose, the reference object 30 is rotated about the first rotation axis 41. This “other” orientation is different from the reference orientation and the current or other orientation can be deduced from the marking 34 in the respective drawings.

FIG. 4B shows the reference object 30 in the first orientation k=1. It is generated from the starting orientation by a 90° rotation about the first rotation axis 41 of the reference object 30. The marking 34 appears in the first other orientation at the left upper corner of the reference object 30. In this first other orientation k=1, the calibration coordinates {right arrow over (r)}_(1j1) of the j reference structures 33 of the first reference object 33 are measured.

FIG. 4C shows the reference object 30 in the second orientation k=2. It is generated by a 180° rotation about a second rotation axis 42 of the reference object 30. The marking 34 appears in the second orientation in the right upper corner of the reference object 30. In this second orientation k=2, the calibration coordinates {right arrow over (r)}_(1j2) of the j reference structures 33 are measured.

FIG. 4D shows the reference object 30 in the third orientation k=3. It is generated from the second orientation by a displacement of the reference object 30 by the vector 43. The marking 34 shows what effect this displacement has on the reference object 30. In this third other orientation k=3, the calibration coordinates {right arrow over (r)}_(1j3) of the j reference structures 33 are measured.

A further embodiment of the self-calibration is illustrated in FIGS. 5A and 5B. FIG. 5A shows analogous to FIG. 4A that initially the reference object 30 is placed on the mask mount in the starting orientation. In this starting orientation k=0 of the reference object 30, the starting coordinates (of the position vector) {right arrow over (r)}_(1j0) of the j selected reference structures 33 are measured. Thereafter, as shown in FIG. 5B, the reference structures 33 of the reference object 30 are measured in at least one other orientation of the reference object 30. For this purpose, the reference object 30 is rotated about a rotation axis 51. This so-called calibration orientation is different from the starting orientation and the current orientation can be derived in FIGS. 5B and 5C from the marking 34.

FIG. 5B shows the reference object 30 in the first calibration orientation k=1. It is generated by a 90° rotation about the rotation axis 51 of the reference object 30. The marking 34 appears in the first calibration orientation in the left upper corner of the reference object 30. In this first calibration orientation k=1, the calibration coordinates {right arrow over (r)}_(1j2) of the j reference structures 33 of the first reference object 33 are measured.

FIG. 5C shows the reference object 30 in the second calibration orientation k=2. It is generated from the orientation of FIG. 5B by a first displacement by the first vector 52 of the reference object 30. The marking 34 appears in the second calibration orientation to be displaced in the left upper corner of the reference object 30. In this second calibration orientation k=2, the calibration coordinates {right arrow over (r)}_(1j2) of the j reference structures 33 are measured.

FIG. 5D shows the reference object 30 in the third calibration orientation k=3. It is generated from the orientation shown in FIG. 5C by a displacement of the reference object 30 by a second vector 53. The marking shows 34 what effect this displacement has on the reference object 30. In this third calibration orientation k=3, the calibration coordinates {right arrow over (r)}_(1j3) of the j reference structures 33 are measured.

It is obvious to a person skilled in the art that the different orientations of the reference object 30 shown in FIGS. 4A to 4D and 5A to 5D can take place in any arbitrary order.

Considered mathematically, a correction function for elimination of the coordinate-dependent measuring errors of a coordinate measuring machine, said correction function being dependent on the measuring location, is a two-dimensional or three-dimensional function {right arrow over (K)}({right arrow over (r)}). In practice, the correction function is always continuous and differentiable. Through use of this correction function {right arrow over (K)}({right arrow over (r)}) on a measured error-laden raw coordinate {right arrow over (r)} (what is meant is the position vector) of a structure of an arbitrary measured object, the associated corrected coordinate {right arrow over (r)}_(korr)={right arrow over (r)}+{right arrow over (K)}({right arrow over (r)}) is obtained.

In order to determine the correction function {right arrow over (K)}({right arrow over (r)}), it is approximated by a series expansion of a set of predetermined fit functions {right arrow over (k)}_(i)({right arrow over (r)}). The following therefore applies:

${\overset{\rightarrow}{K}\left( \overset{\rightarrow}{r} \right)} = {\sum\limits_{i = 0}^{N}{a_{i} \cdot {{\overset{\rightarrow}{k}}_{i}\left( \overset{\rightarrow}{r} \right)}}}$

where a_(i)=fit parameter and N=number of predetermined fit functions {right arrow over (k)}_(i)({right arrow over (r)}).

In order to determine the correction function {right arrow over (K)}({right arrow over (r)}), therefore, the fit parameters a_(i) for the fit functions {right arrow over (k)}_(i)({right arrow over (r)}) must be determined such that the correction is optimal, that is, the residual error is minimal or zero.

The invention is based on the recognition that there are special components of the correction function {right arrow over (K)}({right arrow over (r)}) which are not unambiguously determined or are subject to very large errors. These are largely components which, during calibration measurements of all the orientations of a reference object used for calibration, always coincide with themselves (exactly or approximately), that is, the components with rotational symmetry are invariant for the rotations of the reference object as carried out, and the displacement symmetrical components are invariant for the rotations performed. Each involves a linear combination S(r) of fit functions {right arrow over (k)}_(i)({right arrow over (r)}). The symmetry condition S(r)=D_(k)S(r) then applies. As a special case of the linear combination, this could involve a single identifiable fit function {right arrow over (k)}_(i)({right arrow over (r)}).

These rotationally symmetrical and displacement symmetrical components in the form of the linear combination {right arrow over (S)}({right arrow over (r)}) make no—or a very imprecise—contribution to an approximation of the ideal—exactly right—correction function {right arrow over (K)}({right arrow over (r)}). The correction function would make a contribution, but it cannot be determined from the data. Thus, the presence of such rotationally symmetrical components and displacement symmetrical components lead thereto that the fit parameters a_(i) of the fit functions {right arrow over (k)}_(i)({right arrow over (r)}) cannot be unambiguously determined. In order to improve the error correction, according to the invention, they are therefore removed from the series expansion of the correction function {right arrow over (K)}({right arrow over (r)}).

The invention has been described making reference to particular embodiments. However, it is obvious to a person skilled in the art that derivations and amendments of the invention can be made without thereby departing from the protective scope of the claims that follow. 

1. Method for eliminating basic sources of error in the system correction of a coordinate measuring machine, comprising the following steps: a) that the starting coordinates and the coordinates of the reference structures 33 are determined in a number k>3 of mutually different orientations, for a number j of reference structures 33 on a rigid reference object 30 in a starting orientation k=0 of the reference object 30; b) that the different orientations are generated by at least two rotations about mutually different axes and at least one displacement or by rotation about at least one axis by at least two different displacements;
 2. Method according to claim 1, wherein the calibration coordinates are measured from the calibration orientations generated from the initial orientation, whereby the calibration orientations are generated by the at least two rotations through the rotation functions about the mutually different rotation axes and the displacement function by the least one vector.
 3. Method according to claim 1, wherein the calibration coordinates are measured from the calibration orientations generated from the initial orientation, whereby the calibration orientations are generated by the at least one rotation through the rotation function about the rotation axis and the displacement function by the least vectors.
 4. Method according to one of claims 1 to 3, wherein the starting coordinates and the calibration coordinates are acted upon by a coordinate-dependent correction function, which is described with initially unknown fit parameters and a number N of predetermined, linearly independent fit functions, whereby the calibration coordinates acted upon by the correction function are returned to the starting orientation by means of the respective rotation functions and displacement functions.
 5. Method according to claim 1, wherein the fit parameter is calculated such that for each reference structure 33 all corrected, returned back, and displaced back calibration coordinates and the corrected starting coordinates are in as good agreement as possible.
 6. Method according to claim 5, wherein a continuous correction function to be used on any arbitrary coordinates to be measured is produced, whereby no linear combinations may be formed from their fit functions or from a selection therefrom that coincide with themselves for all performed rotations and displacements
 7. Method according to one of claims 1 to 6, wherein the starting coordinates and the calibration coordinates are measured on the reference object 30 with a first fixed rotation axis 41, and that the starting coordinates and the calibration coordinates are once again measured on the reference object 30 with a second fixed rotation axis 42, and that the starting coordinates and the calibration coordinates are once again measured with a displacement
 43. 8. Method according to one of claims 1 to 6, wherein the starting coordinates and the calibration coordinates are measured on the reference object 30 with a first fixed rotation axis 51, and that the starting coordinates and the calibration coordinates are once again measured with a first fixed displacement 42, and that the starting coordinates and the calibration coordinates are once again measured with a second displacement
 53. 9. Method according to claim 1, wherein a) for the predetermined fit functions, all the rotationally symmetrical linear combinations and displacement symmetrical linear combinations of an arbitrary number P<N of the fit functions are determined with the fit parameters s_(i), which fulfil the symmetry conditions for the rotation functions and the displacement functions; b) that given the existence of a rotationally symmetrical linear combination of this type and a displacement symmetrical linear combination of this type, the previous set of linear independent fit functions is replaced by a new set of linear independent fit functions, wherein these new fit functions are each linear combinations of the previous ones and cover the same function space and wherein one of the new fit functions, specifically that for the displacements and rotations of the reference object is a symmetrical linear combination; c) that the rotationally symmetrical linear combination and the displacement symmetrical linear combination is deleted from the set of fit functions so that their number is then only N−1; d) that the above method steps a), b), c) are repeated until there is no longer a linear combination which fulfils the symmetry conditions for the rotation functions and the displacement function; e) and that using the set of fit functions generated by the M-times repetition of the above method steps a), b), c), the correction function is calculated.
 10. Method according to claim 1, wherein one of the reference objects covers the entire measuring range of the coordinate measuring machine.
 11. Method according to one of the previous claims, wherein the reference object 30 is quadratic and the first rotation axis (41, of 51) runs through its center. 